EASA AD No.: 2012-0144-E

CAP.00111-001 © European Aviation Safety Agency. All rights reserved. 1/2

Proprietary document. Copies are not controlled. Confirm revision status through the EASA-Internet/Intranet.

EASA EMERGENCY AIRWORTHINESS DIRECTIVE

AD No.: 2012-0144-E

Date: 01 August 2012

Note: This Emergency Airworthiness Directive (AD) is issued by EASA, acting in accordance 

with Regulation (EC) No 216/2008 on behalf of the European Community, its Member States 

and of the European third countries that participate in the activities of EASA under Article 66 of 

that Regulation.

This AD is issued in accordance with EC 1702/2003, Part 21A.3B. In accordance with EC 2042/2003 Annex I, Part M.A.301, the 

continuing airworthiness of an aircraft shall be ensured by accomplishing any applicable ADs. Consequently, no person may operate 

an aircraft to which an AD applies, except in accordance with the requirements of that AD, unless otherwise specified by the Agency 

[EC 2042/2003 Annex I, Part M.A.303] or agreed with the Authority of the State of Registry [EC 216/2008, Article 14(4) exemption].

Design Approval Holder’s Name :

EUROCOPTER

Type/Model designation(s) :

EC 225 helicopters

TCDS Number: EASA.R.002

Foreign AD: Not applicable

Revision: None.

ATA 63 Main Rotor Drive – Epicyclic Module/ Chip Detection System –

Check

Manufacturer(s): Eurocopter (formerly EUROCOPTER France)

Applicability: EC 225 LP helicopters, all serial numbers delivered before 01 August 2012 if 

equipped with an epicyclic module Part Number (P/N) 332A32-5021-00 or 

332A32-5021-01.

Reason: The transmission assemblies incorporate a metal chip detection system 

enabling to detect a possible deterioration of a metal component included in 

these assemblies. The tapered housing of the epicyclic module is fitted with a 

magnetic plug located downstream of the collector. This magnetic plug has 

been defined to detect a possible deterioration of the lift bearing belonging to 

the Main Rotor Mast. Thus, after having passed through the collector, these 

chips are carried to the magnetic plug through the oil flow. It was reported that 

the hole joining the integrated collector and the magnetic plug was not a 

through hole. One of the consequence is a functional loss of the magnetic plug 

of the tapered housing. It is then no longer possible to follow up the behaviour 

of the mast bearing through this magnetic plug.

This condition, if not detected and corrected, could result in the loss of control 

of the helicopter.

To address this condition, Eurocopter issued Emergency Alert Service Bulletin 

(EASB) No. 63A011.

For the reasons described above, this AD requires a check for the presence of 

a through hole between the collector integrated in the tapered housing and the 

magnetic plug of the epicyclic module. If a through hole if missing, this AD also 
EASA AD No.: 2012-0144-E

CAP.00111-001 © European Aviation Safety Agency. All rights reserved. 2/2

Proprietary document. Copies are not controlled. Confirm revision status through the EASA-Internet/Intranet.

requires accomplishment of repetitive inspections, and, depending on findings, 

accomplishment of the applicable corrective actions.

Effective Date: 02 August 2012

Required Action(s) 

and Compliance 

Time(s):

Required as indicated, unless accomplished previously:

(1) At the next inspection following the last flight of the day from the effective 

date of this AD, check the hole above the magnetic plug in the epicyclic 

module in accordance with the instructions of Eurocopter EASB No. 

63A011.

(2) If during the check as required by paragraph (1) of this AD, it is detected 

that the hole between the collector integrated in the tapered housing and 

the magnetic plug of the epicyclic module is missing or is not a through

hole, before next flight, and, thereafter, at intervals not too exceed 27,5 

Flight Hours, accomplish a visual inspection for the presence of particles

in accordance with the instructions of Eurocopter EASB No. 63A011.

(3) If during any inspection as required by paragraph (2) of this AD, particles 

are detected, before next flight, contact Eurocopter for an approved 

corrective action.

(4) From the effective date of this AD, do not install an epicyclic module P/N

332A32-5021-00 or 332A32-5021-01 with an EASA Form 1 issued before 

15 August 2012, unless it has passed the check required by paragraph (1) 

of this AD.

Ref. Publications: Eurocopter EC225 EASB No. 63A011 dated 01 August 2012.

The use of later approved revisions of this document is acceptable for 

compliance with the requirements of this AD.

Remarks : 1. If requested and appropriately substantiated, EASA can approve 

Alternative Methods of Compliance for this AD.

2. The results of the safety assessment have indicated the need for 

immediate publication and notification, without the full public consultation 

process.

3. Enquiries regarding this AD should be referred to the Safety Information 

Section, Executive Directorate, EASA. E-mail: ADs@easa.europa.eu.

4. For any question concerning the technical content of the requirements in 

this AD, please contact:

EUROCOPTER (STDI) – Aéroport de Marseille Provence 13725 

Marignane Cedex, France; telephone +33 (4) 42 85 97 97; facsimile +33 

(4) 42 85 99 66; E-mail: Directive.technical-support@eurocopter.com.